TURBOPUMP UNIT Russian patent published in 2017 - IPC F04D13/04 F04D15/02 

FIELD: engines and pumps.

SUBSTANCE: invention can be used in turbopump units of liquid-propellant rocket engines incorporated with multiple-shot rockets. TNA comprises an inlet (1) of reduced pressure, the housing (2) placed therein by a centrifugal pump shaft (3) and the turbine (4) and bearing support (5), the braking device. The braking device is designed as oppositely placed on the housing (2) of the piston chamber (6) in which the rods (9) of the pistons (10) in contact with the turbine disc (4). Pre-piston cavity (7) chamber (6) is communicated with the pump outlet (2) first conduit (11) and through the second conduit (12) and the orifice (13) communicated with the inlet pipe (1), providing a retraction of the stem (9) of the piston (10) from contact with the turbine disc (4) while the TNA. In after-piston cavities (8), chambers (6) are arranged return springs (14).

EFFECT: health preservation bearing turbopump unit under vacuum with repeated exposure to the inclusion LRE, which is achieved by reducing the heating of bearings by reducing run-rotor from operating speed to its full stop.

1 dwg